OPTIMUM DESIGN OF COMPOSITE WING STRUCTURES BY A REFINED OPTIMALITY CRITERION

被引：8

作者：

LIU, IW

LIN, CC

机构：

[1] Institute of Applied Mathematics, National Chung-Hsing University, 40227 Taichung

来源：

COMPOSITE STRUCTURES | 1991年 / 17卷 / 01期

关键词：

Composite Materials;

D O I：

10.1016/0263-8223(91)90060-C

中图分类号：

O3 [力学];

学科分类号：

08 ; 0801 ;

摘要：

Techniques for the optimization of composite with structures are investigated. The refined optimality criterion technique presented in this paper is an algorithm combining a criterion based on the Kuhn-Tucker conditions and the technique of fully stressed design. The main advantages of this method are the generality of use, the efficiency in computation, and the capability of identifying automatically the set of critical constraints. Sensitivity analysis of constraints is based on the virtual load principle. This method is especially suitable for optimum design of large-scale structures. A modular type computer program, ARS 5 (Automatic Resizing System 5), is developed in accordance with the finite element method, refined optimality criterion, sensitivity analysis and Fortran-77 language for the optimization of composite wing structures subjected to sizes, stresses, displacements, twist and buckling constratints. Numerical results for a triple-spars composite wing structure reveal that the present technique is quite efficient and reliable. © 1990.

引用

页码：51 / 65

页数：15

共 11 条

[1]

Khot, Computer program (OPTCOMP) for optimization of composite structures for minimum weight design, AFFDL-TR-76-149, (1977)

[2]

Venkayya, Tishler, OPTSTAT — A computer program for optimal design of structures subjected to static loads, AFFDL-TR-79-67, (1979)

[3]

Schmit, Ramanathan, A multilevel approach for minimum weight structural design including local and system buckling constraints, AIAA Paper 77-373, (1977)

[4]

Starnes, Haftka, Preliminary design of composite wings for buckling, strength, and displacement constraints, Journal of Aircraft, 16, 8, pp. 564-570, (1979)

[5]

Lin, Liu, Optimal design based on optimality criterion for frame structures including buckling constraints, Computers & Structures, 31, 4, pp. 535-544, (1989)

[6]

Lin, Liu, A mixed optimality criterion technique applied to aircraft wing structural design, Proceedings of the fourth SAS-World Conference FEMCAD, 2, pp. 136-143, (1988)

[7]

Razani, Behavior of fully stressed design structures and its relationships to minimum weights design, AIAA Journal, 3, 12, pp. 2262-2268, (1965)

[8]

Ashton, Whitney, Theory of Laminated Plates, (1970)

[9]

Jones, Mechanics of Composite Materials, (1975)

[10]

Stroud, Agranoff, Minimum-mass design of filamentary composite panels under combined loads: Design procedure based on simplified buckling equations, NASA TN D-8257, (1976)

← 1 2 →